CN114322682A - Test system and method based on patrol missile launching impact overload - Google Patents
Test system and method based on patrol missile launching impact overload Download PDFInfo
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Abstract
The invention relates to the technical field of overload testing, and discloses a testing system and a method based on patrol missile launching impact overload, which comprises the following steps: the overload testing device is arranged on the patrol missile, the mass center of the overload testing device is matched with that of the patrol missile, and the overload testing device is connected with the patrol missile through the conformal end surface; the overload testing device comprises a first accelerometer, a second accelerometer and a data acquisition board, and the first accelerometer and the second accelerometer are both connected with the data acquisition board; the first accelerometer is used for acquiring first acceleration information of the patrol missile in the flight process and sending the first acceleration information to the data acquisition board; and the second accelerometer is used for acquiring second acceleration information of the patrol missile in the flight process and sending the second acceleration information to the data acquisition board.
Description
Technical Field
The invention relates to the technical field of overload testing, in particular to a test system and a test method based on patrol missile launching impact overload.
Background
The flying patrol bomb has the characteristics of miniaturization, individual soldier and low cost, so the flying patrol bomb is often used for executing comprehensive tasks. In the development process of small-sized flying patrol bombs, the data of flying patrol bomb launching impact overload is a key part for analyzing the dynamic behavior and the structure dynamic response rule of the flying patrol bombs, and data support is provided for the impact vibration design of a system on the bomb. Therefore, the method is very important for optimizing a scheme of a flying round launching system, designing the adaptability of the full-elasticity mechanical environment and the like. A full bomb circuit of a small-sized flying patrol bomb is complex, a lead needs to be led out to transmit signals in the traditional bomb internal acceleration testing method, and the accuracy of data acquisition is affected by charged gas and interference signals in the launching process. The overload instantaneous overload value of the small-sized patrol missile is large, the maneuvering capability in the operation process is strong, the patrol missile can bear overload of different degrees in the working process, and the required overload value needs to be reserved through threshold sampling. The overall structure of small-size round of flying bullet is inseparable, and the barycenter changes and can influence the consumption that increases the projectile body flight in-process. At present, the number of embedded hardware system modules for measuring overload is large, the number of peripheral circuits is large, and the installation positions are different, but the electromagnetic influence on the whole circuit of the projectile body in the running process of an overload test system and the influence of the installation of an overload test device on the mass center of the whole projectile body are not considered in the existing method, so that the measurement error is large.
Disclosure of Invention
The invention provides a test system and a test method based on patrol missile launching impact overload, and aims to solve the problem that an existing overload test system is large in measurement error.
In order to achieve the purpose, the invention is realized by the following technical scheme:
in a first aspect, the present invention provides a test system based on a round missile launching impact overload, including: the overload testing device is arranged on the patrol missile, the mass center of the overload testing device is matched with that of the patrol missile, and the overload testing device is connected with the patrol missile through the conformal end surface;
the overload testing device comprises a first accelerometer, a second accelerometer and a data acquisition board, and the first accelerometer and the second accelerometer are both connected with the data acquisition board;
the first accelerometer is used for acquiring first acceleration information of the patrol missile in the flight process and sending the first acceleration information to the data acquisition board;
the second accelerometer is used for acquiring second acceleration information of the patrol missile in the flight process and sending the second acceleration information to the data acquisition board;
the data acquisition board is used for storing the first acceleration information and the second acceleration information.
Optionally, a counterweight is arranged on the overload testing device, and the counterweight is used for increasing the weight of a partial area of the overload testing device so as to adjust the centroid of the overload testing device to be located at the geometric center of the overload testing device.
Optionally, be provided with first through-hole and second through-hole on patrolling the body of missile, overload testing arrangement passes through first through-hole with the second through-hole with patrolling the missile and connecting, first through-hole with the second through-hole is based on the barycenter symmetry of body.
Optionally, the data acquisition board further includes a storage module, and the storage module is connected to the first accelerometer and the second accelerometer respectively.
Optionally, the system further comprises an upper computer, wherein the upper computer is in communication connection with the data acquisition board;
the upper computer is used for sending a control instruction to the data acquisition board, and the control instruction comprises a query instruction, a receiving instruction or an erasing instruction;
the data acquisition board is also used for receiving the control instruction, and under the condition that the control instruction is a query instruction, the data acquisition board queries data stored in a storage module based on the query instruction; under the condition that the control instruction is a receiving instruction, the data acquisition board sends data stored in the storage module to an upper computer; and under the condition that the control instruction is an erasing instruction, the data acquisition board erases data stored in the storage module.
Optionally, the overload testing apparatus further includes a power supply module, and the power supply module is connected to the data acquisition board.
In a second aspect, an embodiment of the present application provides a test method based on a round missile launching impact overload, including:
the first accelerometer collects first acceleration information of the patrol missile in the flight process and sends the first acceleration information to the data acquisition board;
the second accelerometer collects second acceleration information of the patrol missile in the flight process and sends the second acceleration information to the data acquisition board;
the data acquisition board stores the first acceleration information and the second acceleration information.
Optionally, the data acquisition board further includes a storage module, and after the data acquisition board stores the first acceleration information and the second acceleration information, the method further includes:
the data acquisition board records the first acceleration information and the second acceleration information in a queue with a preset time length, and stores data stored in the current queue into the storage module under the condition that the average value of N records exceeds a preset threshold value, wherein N is a positive integer.
In a third aspect, an embodiment of the present application provides an upper computer, the upper computer is in communication connection with the data acquisition board, the upper computer is applied to the method steps according to the second aspect, and the method further includes:
the upper computer sends a control instruction to the data acquisition board, wherein the control instruction comprises a query instruction, a receiving instruction or an erasing instruction;
the data acquisition board also receives the control instruction, and under the condition that the control instruction is a query instruction, the data acquisition board queries data stored in a storage module based on the query instruction; under the condition that the control instruction is a receiving instruction, the data acquisition board sends data stored in the storage module to an upper computer; and under the condition that the control instruction is an erasing instruction, the data acquisition board erases data stored in the storage module.
Has the advantages that:
according to the test system and method based on missile launching impact overload, the overload test device is connected with the patrol missile through the conformal end face, so that the overload test device can be stably arranged in the patrol missile, the position of the mass center of the overload test device is adjusted through moving the counter weight in the overload test device, and the position of the mass center of the overload test device is always matched with the position of the mass center of the patrol missile, so that the stability of the overload test device is guaranteed, the situation of large test error is avoided, meanwhile, the conformal end face can be replaced, so that the test system and method are suitable for missiles with different calibers of the patrol missile, and the adaptability of the device is improved.
Drawings
Fig. 1 is a schematic structural diagram of a test system based on a round missile launching impact overload according to a preferred embodiment of the present invention;
FIG. 2 is a schematic diagram of the connection between the flying round and the overload testing device according to the preferred embodiment of the invention;
FIG. 3 is a functional diagram of a host computer according to a preferred embodiment of the present invention;
fig. 4 is a schematic diagram of a test method based on a round missile launching impact overload according to a preferred embodiment of the present invention.
Reference numerals:
1. b, flying round; 2. counting the mining plates; 3. a power supply module; 4. and a balancing weight.
Detailed Description
The technical solutions of the present invention are described clearly and completely below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Unless defined otherwise, technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs. The use of "first," "second," and similar terms in the present application do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships are changed accordingly.
Referring to fig. 1, an embodiment of the present application provides a test system based on a missile 1 launching impact overload, including: the device comprises a flying patrol bomb 1, an overload testing device and a conformal end face, wherein the overload testing device is arranged on the flying patrol bomb 1, the mass center of the overload testing device is matched with the mass center of the flying patrol bomb 1, and the overload testing device is connected with the flying patrol bomb 1 through the conformal end face;
the overload testing device comprises a first accelerometer, a second accelerometer and a data acquisition board 2, wherein the first accelerometer and the second accelerometer are both connected with the data acquisition board 2;
the first accelerometer is used for acquiring first acceleration information of the patrol missile 1 in the flight process and sending the first acceleration information to the data acquisition board 2;
the second accelerometer is used for acquiring second acceleration information of the patrol missile 1 in the flight process and sending the second acceleration information to the data acquisition board 2;
the data acquisition board 2 is used for storing first acceleration information and second acceleration information.
In this embodiment, the main processor of the data acquisition board 2 may be an STM32F411xC type of an ARM 32-bit Cortex-M4 architecture microprocessor, the processor main frequency is 125DMIPS, and the data acquisition board has a self-adaptive implementation accelerator, integrates an MCU and an FPU instruction, supports all ARM single-precision data processing instructions and data types, and effectively improves the execution speed and code efficiency of a control algorithm; a set of complete DSP instructions and a memory protection unit MPU are arranged in the processor, so that the safety of an application program is enhanced; the innovative function of a Batch Acquisition Model (BAM) is added into the processor, so that more energy consumption can be saved in data batch processing; this is by way of example only and not by way of limitation.
In this embodiment, the accelerometers can be MEAS832-0200 type accelerometer and MEAS834M1-6000 type accelerometer, MEAS832-0200 type accelerometer is a low cost, board mounted tri-axial accelerometer, with stable piezoelectric ceramic crystal, maximum current consumption less than 4uA, testable impact force range from + -25 g to + -500 g, and can provide response frequency up to 2000Hz, size of 18.8mm × 14.48mm × 4.3mm, mass of only 3.6 g; the MEAS834M1-60000 type accelerometer is a low-cost, plate-mounted triaxial accelerometer, can measure the range of impact force to be up to +/-2000 g to +/-6000 g, is an accelerometer specially designed for high-benefit embedded impact application, can provide response frequency up to 6000Hz, has the maximum current consumption of 22uA, has the working temperature range of-40 ℃ to +125 ℃, has the size of 18.8mm multiplied by 14.48mm multiplied by 4.3mm and has the mass of only 2.6 g; this is by way of example only and not by way of limitation.
Utilize conformal terminal surface to install overload test device on patrolling missile 1, make overload test device can stably locate the inside of patrolling missile 1, guaranteed overload test's stability, avoid appearing the great condition of measuring error, conformal terminal surface can be changed simultaneously, can adapt to the body of patrolling the missile 1 different bores to the adaptability of the device has been improved.
The data acquisition board 2 further comprises a storage module, and the storage module is respectively connected with the first accelerometer and the second accelerometer.
The data that first accelerometer and second accelerometer record can be transmitted and be stored in the storage module that sets up in the data acquisition board 2, can store the data that the test obtained through storage module technique, still conveniently call the data of storage at any time simultaneously.
The overload testing device also comprises a power supply module 3, and the power supply module 3 is connected with the data acquisition board 2.
The power supply module 3 can supply power for the data acquisition board 2 in the overload testing device, so that the normal work of the data acquisition board 2 is ensured.
Referring to fig. 2, a weight block 4 is disposed on the overload testing device, and the weight block 4 is used to increase the weight of a partial region of the overload testing device so as to adjust the centroid of the overload testing device to be located at the geometric center of the overload testing device.
Overload test device can change overload test device self barycenter position through removing balancing weight 4, when overload test device's barycenter position and the barycenter position of patrolling missile 1 when the deviation appears, alright make the position of overload test device barycenter identical with the position of patrolling missile 1 barycenter through the position of removing balancing weight 4.
Be provided with first through-hole and second through-hole on patrolling the body of missile 1, overload testing arrangement is connected with patrolling missile 1 through first through-hole and second through-hole, and first through-hole and second through-hole are based on the barycenter symmetry of body.
The first through hole and the second through hole can be restricted to overload testing arrangement and the mounting means and the mounted position of patrolling between the missile 1, avoid patrolling missile 1 at the in-process of flight motion, and overload testing arrangement takes place to remove in the position of patrolling on missile 1, cause the influence to measured precision.
Referring to fig. 3, the above-mentioned testing system based on the round missile 1 launches the impact overload, further includes: the upper computer is in communication connection with the data acquisition board 2;
the upper computer is used for sending control instructions to the data acquisition board 2, and the control instructions comprise query instructions, receiving instructions or erasing instructions;
the data acquisition board 2 is also used for receiving a control instruction, and under the condition that the control instruction is a query instruction, the data acquisition board 2 queries data stored in the storage module based on the query instruction; under the condition that the control instruction is a receiving instruction, the data acquisition board 2 sends the data stored in the storage module to an upper computer; in the case where the control command is an erase command, the data acquisition board 2 erases data stored in the storage module.
The upper computer controls the data acquisition board 2, a control instruction is sent to the data acquisition board 2 through the upper computer, and after the data acquisition board 2 receives the control instruction, corresponding operation can be carried out according to the content indicated by the control instruction.
In one example, after the data acquisition board 2 is powered on, the chip in the data acquisition board 2 is initialized, the upper computer is in communication butt joint with the data acquisition board 2, the data acquisition board 2 enters a countdown starting stage, a timer of 200ms is started inside, the data acquisition board 2 monitors state data of two accelerometers in the process of launching the flying bomb 1 in real time, and an internal double-buffer area is opened to store the monitoring data; the two accelerometers can convert 6 paths of data into 6 paths of AD data through the ADC module, the digitizer can record the data after reading the 6 paths of AD data, and judge whether the acceleration exceeds a threshold value or not through the average value of 10 times of stored data, and the data exceeding the threshold value is transferred to the storage module; the upper computer sends a data storage amount instruction for entering a FLASH mode and inquiring a storage module in the data acquisition board 2, the data acquisition board 2 enters the FLASH mode and feeds back the data amount stored in the corresponding storage module of the upper computer, and if a certain amount of data is stored in the storage module, the following operations can be carried out; after the upper computer sends and receives the instruction of the data of the storage module, the data acquisition board 2 returns 6 paths of AD data collected and read by the accelerometer and is received by the upper computer, and the upper computer can store and analyze the data after receiving the 6 paths of AD data; after the upper computer sends an instruction for erasing the data of the storage module, the data acquisition board 2 erases the data stored in the storage module and sends a feedback signal to the upper computer after all the data are erased for the upper computer to perform subsequent operation processing; in the flying process of the patrol bomb 1, the data acquisition board 2 can continuously record and store the overload value reaching the threshold value, and after the patrol bomb 1 is recovered, the upper computer is in butt joint with the overload testing device, so that the data recorded in the storage module in the data acquisition board 2 can be read;
the upper computer can draw a data curve and calibrate the maximum value and the minimum value through the obtained data, and calculates the initial speed of the projectile body according to the obtained data.
Referring to fig. 4, an embodiment of the present application further provides a method for testing a launch impact overload based on a flying round 1, including:
the method comprises the following steps that a first accelerometer collects first acceleration information of a flying patrol bomb 1 in a flying process and sends the first acceleration information to a data acquisition board 2;
the second accelerometer collects second acceleration information of the patrol missile 1 in the flying process and sends the second acceleration information to the data acquisition board 2;
the data acquisition board 2 stores first acceleration information and second acceleration information.
The optional test method based on the patrol missile 1 launching impact overload further comprises the following steps:
the data acquisition board 2 records the first acceleration information and the second acceleration information in a queue with a preset time length, and stores data stored in the current queue into a storage module under the condition that the average value of N times of records exceeds a preset threshold value, wherein N is a positive integer.
The optional test method based on the patrol missile 1 launching impact overload further comprises the following steps:
the upper computer sends a control instruction to the data acquisition board 2, wherein the control instruction comprises a query instruction, a receiving instruction or an erasing instruction;
the data acquisition board 2 also receives a control instruction, and under the condition that the control instruction is a query instruction, the data acquisition board 2 queries data stored in the storage module based on the query instruction; under the condition that the control instruction is a receiving instruction, the data acquisition board 2 sends the data stored in the storage module to an upper computer; in the case where the control command is an erase command, the data acquisition board 2 erases data stored in the storage module.
The method for testing the launching impact overload based on the patrol missile 1 can realize various embodiments of the system for testing the launching impact overload based on the patrol missile 1, and can achieve the same beneficial effects, and the detailed description is omitted here.
In using the present application: the overload testing device is arranged on the flying bomb 1 through the conformal end face, the position of a balancing weight 4 on the overload testing device is adjusted, the position of the mass center of the overload testing device is matched with the position of the mass center of the flying bomb 1, the stability of overload testing is guaranteed, the situation of large measurement error is avoided, when the overload testing device starts to work, a power supply module 3 supplies electric energy to a data acquisition board 2 to ensure the data acquisition board 2 to work normally, a first accelerometer and a second accelerometer collect first acceleration information and second acceleration information of the flying bomb 1 in the flying process and respectively send the first acceleration information and the second acceleration information to a storage module in a digital board for storage, at the moment, a worker operates an upper computer and sends a control instruction to the data acquisition board 2 through the upper computer, the control instruction comprises an inquiry instruction, a receiving instruction or an erasing instruction, after receiving the control command, the data acquisition board 2 can perform corresponding operation according to the type of the control command;
when the control instruction is a query instruction, the data stored in the storage module is queried;
when the control instruction is a receiving instruction, the data acquisition board 2 sends the data stored in the storage module back to the upper computer;
when the control command is an erasing command, the digital board erases the data stored in the storage module.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (9)
1. The utility model provides a test system based on patrol missile launch and strike overload which characterized in that includes: the overload testing device is arranged on the patrol missile, the mass center of the overload testing device is matched with that of the patrol missile, and the overload testing device is connected with the patrol missile through the conformal end surface;
the overload testing device comprises a first accelerometer, a second accelerometer and a data acquisition board, and the first accelerometer and the second accelerometer are both connected with the data acquisition board;
the first accelerometer is used for acquiring first acceleration information of the patrol missile in the flight process and sending the first acceleration information to the data acquisition board;
the second accelerometer is used for acquiring second acceleration information of the patrol missile in the flight process and sending the second acceleration information to the data acquisition board;
the data acquisition board is used for storing the first acceleration information and the second acceleration information.
2. The round missile launch impact overload-based test system according to claim 1, wherein a counterweight is arranged on the overload test device, and the counterweight is used for increasing the weight of a partial area of the overload test device so as to adjust the centroid of the overload test device to be located at the geometric center of the overload test device.
3. The system according to claim 1, wherein a first through hole and a second through hole are formed in the projectile body of the projectile, the overload testing device is connected with the projectile body through the first through hole and the second through hole, and the first through hole and the second through hole are symmetrical based on the mass center of the projectile body.
4. The round missile launch impact overload-based test system of claim 1, wherein the data acquisition board further comprises a storage module, and the storage module is respectively connected with the first accelerometer and the second accelerometer.
5. The patrol missile launch impact overload-based test system according to claim 1, further comprising an upper computer, wherein the upper computer is in communication connection with the data acquisition board;
the upper computer is used for sending a control instruction to the data acquisition board, and the control instruction comprises a query instruction, a receiving instruction or an erasing instruction;
the data acquisition board is also used for receiving the control instruction, and under the condition that the control instruction is a query instruction, the data acquisition board queries data stored in a storage module based on the query instruction; under the condition that the control instruction is a receiving instruction, the data acquisition board sends data stored in the storage module to an upper computer; and under the condition that the control instruction is an erasing instruction, the data acquisition board erases data stored in the storage module.
6. The round missile launch impact overload-based testing system of claim 1, wherein the overload testing device further comprises a power supply module, and the power supply module is connected with the data acquisition board.
7. A method for testing the missile-based missile impact overload, which is applied to the system for testing the missile-based missile impact overload according to any one of claims 1 to 6, and is characterized by comprising the following steps:
the first accelerometer collects first acceleration information of the patrol missile in the flight process and sends the first acceleration information to the data acquisition board;
the second accelerometer collects second acceleration information of the patrol missile in the flight process and sends the second acceleration information to the data acquisition board;
the data acquisition board stores the first acceleration information and the second acceleration information.
8. The round-the-fly missile launch impact overload-based testing method according to claim 7, wherein the data acquisition board further comprises a storage module, and after the data acquisition board stores the first acceleration information and the second acceleration information, the method further comprises:
the data acquisition board records the first acceleration information and the second acceleration information in a queue with a preset time length, and stores data stored in the current queue into the storage module under the condition that the average value of N records exceeds a preset threshold value, wherein N is a positive integer.
9. The patrol missile launch impact overload-based test method according to claim 7, wherein the patrol missile launch impact overload-based test system further comprises an upper computer, the upper computer is in communication connection with the data acquisition board, and the method further comprises:
the upper computer sends a control instruction to the data acquisition board, wherein the control instruction comprises a query instruction, a receiving instruction or an erasing instruction;
the data acquisition board also receives the control instruction, and under the condition that the control instruction is a query instruction, the data acquisition board queries data stored in a storage module based on the query instruction; under the condition that the control instruction is a receiving instruction, the data acquisition board sends data stored in the storage module to an upper computer; and under the condition that the control instruction is an erasing instruction, the data acquisition board erases data stored in the storage module.
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| CN110595426A (en) * | 2019-10-11 | 2019-12-20 | 北京理工大学 | System and method for measuring missile-borne angle |
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